CA933369A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
CA933369A
CA933369A CA113016A CA113016A CA933369A CA 933369 A CA933369 A CA 933369A CA 113016 A CA113016 A CA 113016A CA 113016 A CA113016 A CA 113016A CA 933369 A CA933369 A CA 933369A
Authority
CA
Canada
Prior art keywords
gas turbine
turbine engine
engine
gas
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
CA113016A
Inventor
M. Denning Ralph
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Application granted granted Critical
Publication of CA933369A publication Critical patent/CA933369A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
CA113016A 1970-05-16 1971-05-14 Gas turbine engine Expired CA933369A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB2383970 1970-05-16
GB3193770 1970-07-01

Publications (1)

Publication Number Publication Date
CA933369A true CA933369A (en) 1973-09-11

Family

ID=26256753

Family Applications (1)

Application Number Title Priority Date Filing Date
CA113016A Expired CA933369A (en) 1970-05-16 1971-05-14 Gas turbine engine

Country Status (4)

Country Link
US (1) US3761042A (en)
CA (1) CA933369A (en)
DE (1) DE2122762C3 (en)
FR (1) FR2090085B1 (en)

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1443333A (en) * 1972-08-12 1976-07-21 Mtu Muenchen Gmbh Aircraft having apparatus for augmenting the lift of the aircraft
US3893638A (en) * 1974-02-14 1975-07-08 Boeing Co Dual cycle fan jet engine for stol aircraft with augmentor wings
US3936226A (en) * 1974-06-07 1976-02-03 United Technologies Corporation Control system for variable pitch fan propulsor with reverse pitch
US3932058A (en) * 1974-06-07 1976-01-13 United Technologies Corporation Control system for variable pitch fan propulsor
US4222234A (en) * 1977-07-25 1980-09-16 General Electric Company Dual fan engine for VTOL pitch control
GB2469612B (en) * 1980-11-26 2011-03-23 Rolls Royce Plc V STOL Aircraft
JPS62201828A (en) * 1986-02-28 1987-09-05 Suntory Ltd Supercritical extraction process and apparatus therefor
EP2074321B1 (en) * 2006-10-12 2012-12-05 United Technologies Corporation Fan variable area nozzle with adaptive structure and method of varying a fan exit area of a gas turbine engine
US10041442B2 (en) * 2010-06-11 2018-08-07 United Technologies Corporation Variable area fan nozzle
US8777793B2 (en) 2011-04-27 2014-07-15 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US20130192198A1 (en) 2012-01-31 2013-08-01 Lisa I. Brilliant Compressor flowpath
US20130239542A1 (en) * 2012-03-16 2013-09-19 United Technologies Corporation Structures and methods for intercooling aircraft gas turbine engines
GB201419756D0 (en) 2014-11-06 2014-12-24 Rolls Royce Plc Bleed valve

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3123322A (en) * 1964-03-03 Aircraft power plant
CA502548A (en) * 1954-05-18 Armstrong Siddeley Motors Limited Control of propeller gas-turbine engines for aircraft
GB757981A (en) * 1952-02-06 1956-09-26 Rolls Royce Improvements in or relating to gas turbine engines
GB881662A (en) * 1957-01-29 1961-11-08 Bristol Siddeley Engines Ltd Improvements in or relating to gas turbine jet propulsion engine units for aircraft and also jet propelled aircraft
US3008515A (en) * 1957-05-28 1961-11-14 Gen Motors Corp Fuel control
US3054254A (en) * 1959-01-27 1962-09-18 United Aircraft Corp Turbofan afterburner fuel control improvement
US3108767A (en) * 1960-03-14 1963-10-29 Rolls Royce By-pass gas turbine engine with air bleed means
DE1198131B (en) * 1964-02-12 1965-08-05 Daimler Benz Ag Dual-circuit gas turbine jet engine
FR1483852A (en) * 1966-04-12 1967-06-09 Marchetti Soc Charles Power unit suitable in particular for driving a combined, jet helicopter
US3356152A (en) * 1966-06-14 1967-12-05 North American Aviation Inc Aircraft propulsion system
GB1195964A (en) * 1966-12-05 1970-06-24 Rolls Royce Fan.
GB1175066A (en) * 1966-12-12 1969-12-23 Westland Aircraft Ltd Improvements in or relating to Vertical Take-Off and Landing Aircraft
GB1294324A (en) * 1969-05-03 1972-10-25 Dowty Rotol Ltd Engine installations
US3604662A (en) * 1970-01-19 1971-09-14 Rohr Corp Thrust-reversing apparatus for jet-propelled aircraft

Also Published As

Publication number Publication date
DE2122762C3 (en) 1975-01-02
US3761042A (en) 1973-09-25
FR2090085A1 (en) 1972-01-14
FR2090085B1 (en) 1975-08-01
DE2122762B2 (en) 1974-05-22
DE2122762A1 (en) 1971-12-02

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